26484 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules 

30CEE High Efficiency Residential Swimming 

Pool Initiative, Consortium of Energy Efficiency. 

Available at http://library.cee1.org/sites/default/

files/library/9986/cee_res_swimmingpoolinitiative_

07dec2012_pdf_10557.pdf. 

31Size standards, listed by NAICS code and 

industry description and are available at http://

www.sba.gov/category/navigation-structure/

contracting/contracting-officials/smallbusinesssize-standards. 

Issue 28: DOE seeks comment 

regarding the typical energy use of 

dedicated-purpose pool pumps. If 

available, DOE requests that these data 

be broken-out by equipment type, hp 

(rated nameplate hp or THP), operating 

speed, application, and any other 

parameters relevant to the pool pump 

industry. 

Issue 29: A study by CEE 30 estimates 

that adopting higher efficiency 

technologies, such as multi-speed and 

variable-speed pool pumps, may result 

in energy savings of 1,900–3,800 kWh/ 

year for each residential swimming pool 

pump. DOE seeks comment on whether 

the approach and assumptions 

described in that report would be 

appropriate to use as a basis for 

estimating national energy savings, and 

on the accuracy of the estimates 

themselves. If so, why? If not, why not? 

Issue 30: The pool pump industry 

defines ‘‘turnover rate’’ as the total 

number of times the entire volume of 

water in the pool is circulated (or 

‘‘turned over’’) within a 24-hour period. 

The industry defines ‘‘turnover time’’ as 

the amount of time required to circulate 

the entire volume of water in the pool 

once. Turnover rate is calculated by 

dividing 24 hours by the turnover time 

in hours. DOE seeks comment on typical 

turnover rates and times, as well as any 

variation by application, state, or 

climate region. 

Issue 31: DOE seeks comment on the 

usage profiles of dedicated-purpose pool 

pumps broken-out by climate, pool or 

pump type (i.e., inground or 

aboveground, indoor or outdoor), hp 

(rated nameplate hp or THP), and 

efficiency. DOE is specifically interested 

in hours of use per day at each speed 

when multi-speed or variable-speed 

pumps are used. 

Issue 32: DOE seeks data and 

comment on the number of months per 

year that dedicated-purpose pool pumps 

typically operate, broken-out by state or 

climate region. 

Issue 33: DOE requests comment on 

the typical lifetime of dedicatedpurpose pool pumps. 

3. Manufacturer Impact Analysis 

Issue 34: DOE seeks to identify all 

dedicated-purpose pool pump 

manufacturers that currently distribute 

equipment in the United States. 

Currently, DOE has identified Pentair 

Ltd., Hayward Industries, Inc., Zodiac, 

Speck Pumps, and Waterway Plastics as 

dedicated-purpose pool pump 

manufacturers. DOE seeks comment on 

the comprehensiveness of this list of 

manufacturers, and requests the names 

and contact information of any other 

domestically- or foreign-based 

manufacturers that sell or otherwise 

market their dedicated-purpose pool 

pumps in the United States. 

Issue 35: DOE seeks to identify all 

dedicated-purpose pool pump 

manufacturers that currently distribute 

equipment in the United States who 

also qualify as small businesses. The 

Small Business Administration (SBA) 

defines a small business under North 

American Industry Classification 

System (NAICS) code 333911, ‘‘Pump 

and Pumping Equipment 

Manufacturing,’’ as one having no more 

than 500 employees.31 DOE requests the 

names of any small business 

manufacturers of dedicated-purpose 

pool pumps that it should consider in 

its analysis. 

III. Public Participation 

DOE will accept comments, data, and 

information regarding this RFI and other 

matters relevant to DOE’s consideration 

of any energy conservation standards for 

dedicated-purpose pool pumps by June 

22, 2015. After the close of the comment 

period, DOE will begin collecting data, 

conducting the analyses, and reviewing 

the public comments. These actions will 

be taken to aid in the consideration of 

a rulemaking for dedicated-purpose 

pool pumps. 

Instructions: All submissions received 

must include the agency name and 

docket number and/or RIN for this 

rulemaking. No telefacsimilies (faxes) 

will be accepted. 

Docket: The docket is available for 

review at www.regulations.gov, 

including Federal Register notices, 

public meeting attendees’ lists and 

transcripts, comments, and other 

supporting documents/materials. All 

documents in the docket are listed in 

the www.regulations.gov index. 

However, not all documents listed in 

the index may be publicly available, 

such as information that is exempt from 

public disclosure. 

A link to the docket Web page can be 

found at: http://www.regulations.gov/

#!docketDetail;D=EERE-2015-BT-STD0008. This Web page contains a link to 

the docket for this notice on the 

www.regulations.gov Web site. The 

www.regulations.gov Web page contains 

simple instructions on how to access all 

documents, including public comments, 

in the docket. 

For information on how to submit a 

comment, or review other public 

comments and the docket, contact Ms. 

Brenda Edwards at (202) 586–2945 or by 

email: Brenda.Edwards@ee.doe.gov. 

DOE considers public participation to 

be a very important part of the process 

for developing test procedures. DOE 

actively encourages the participation 

and interaction of the public during the 

comment period in each stage of the 

rulemaking process. Interactions with 

and between members of the public 

provide a balanced discussion of the 

issues and assist DOE in the rulemaking 

process. Anyone who wishes to be 

added to the DOE mailing list to receive 

future notices and information about 

this rulemaking should contact Ms. 

Brenda Edwards at (202) 586–2945, or 

via email at Brenda.Edwards@

ee.doe.gov. 

Issued in Washington, DC, on April 24, 

2015. 

Kathleen Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency, Energy Efficiency and Renewable 

Energy. 

[FR Doc. 2015–11011 Filed 5–7–15; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1279; Directorate 

Identifier 2014–NM–049–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

SYSTEMS (Operations) Limited 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2011–21– 

06 for all BAE SYSTEMS (Operations) 

Limited Model 4101 airplanes. AD 

2011–21–06 currently requires revising 

the maintenance program. Since we 

issued AD 2011–21–06, we have 

determined that the life limit of certain 

main landing gear components must be 

reduced, and certain post-repair 

inspections of critical structure are 

necessary. This proposed AD would 

require a new revision of the 

maintenance/inspection program. We 

are proposing this AD to prevent failure 

of certain structurally significant items, 


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including the main landing gear and 

nose landing gear, which could result in 

reduced structural integrity of the 

airplane; and to prevent fuel vapor 

ignition sources, which could result in 

a fuel tank explosion and consequent 

loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 22, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact BAE 

SYSTEMS (Operations) Limited, 

Customer Information Department, 

Prestwick International Airport, 

Ayrshire, KA9 2RW, Scotland, United 

Kingdom; telephone +44 1292 675207; 

fax +44 1292 675704; email 

RApublications@baesystems.com; 

Internet http://www.baesystems.com/

Businesses/RegionalAircraft/index.htm. 

You may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1279; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: 425–227–1175; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–1279; Directorate Identifier 

2014–NM–049–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On September 23, 2011, we issued AD 

2011–21–06, Amendment 39–16829 (76 

FR 64788, October 19, 2011). AD 2011– 

21–06 requires actions intended to 

address an unsafe condition on BAE 

SYSTEMS (Operations) Limited Model 

4101 airplanes. 

Since we issued AD 2011–21–06, 

Amendment 39–16829 (76 FR 64788, 

October 19, 2011), we have determined 

that the life limit of certain main 

landing gear components must be 

reduced, and new inspections of certain 

repairs that affect fatigue strength of 

critical structure must be added to the 

maintenance/inspection program. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0043, dated February 21, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

The Jetstream J41 Aircraft Maintenance 

Manual (AMM), includes the following 

chapters: 

05–10–10 ‘‘Airworthiness Limitations’’, 

05–10–20 ‘‘Certification Maintenance 

Requirements’’, and, 

05–10–30 ‘‘Critical Design Configuration 

Control Limitations (CDCCL)—Fuel System’’. 

The maintenance tasks and limitations 

contained in these chapters have been 

identified as mandatory actions for continued 

airworthiness and EASA issued AD 2010– 

0098 [dated May 27, 2010 (http://

ad.easa.europa.eu/ad/2010-0098) which 

corresponds to FAA AD 2011–21–06, 

Amendment 39–16829 (79 FR 64788, October 

19, 2011)] to require operators to comply 

with those instructions. 

Since that [EASA] AD was issued, BAE 

Systems (Operations) Ltd issued Revision 37 

of the AMM amending Chapter 05–10–10 to 

revise and reduce the life limit of certain 

main landing gear components. In addition, 

Revision 38 of the AMM was issued to 

amend Chapters 05–10–00 and 05–10–10 

introducing inspections to be accomplished 

after implementation of some repairs 

affecting fatigue strength of critical structure. 

Failure to comply with the new and more 

restrictive actions could result in an unsafe 

condition. 

For the reasons described above, this 

[EASA] AD, which supersedes EASA AD 

2010–0098, requires implementation of the 

maintenance requirements and/or 

airworthiness limitations as specified in the 

defined parts of Chapter 05 of the AMM at 

Revision 38. 

The unsafe condition is the failure of 

certain structurally significant items, 

including the main landing gear and 

nose landing gear, which could result in 

reduced structural integrity of the 

airplane; and fuel vapor ignition 

sources, which could result in a fuel 

tank explosion and consequent loss of 

the airplane. You may examine the 

MCAI in the AD docket on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2015–1279. 

Related Service Information Under 1 

CFR Part 51 

BAE SYSTEMS (Operations) Limited 

has issued Subjects 05–10–10, 

‘‘Airworthiness Limitations’’; 05–10–20, 

‘‘Certification Maintenance 

Requirements’’; and 05–10–30, ‘‘Critical 

Design Configuration Control 

Limitations (CDCCL)—Fuel System’’; of 

Chapter 05, ‘‘Airworthiness 

Limitations,’’ of the BAE Systems 

(Operations) Limited J41 AMM, 

Revision 38, dated September 15, 2013, 

which describe procedures for 

inspections of structurally significant 

items and the fuel system. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section of this NPRM. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 


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information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 4 airplanes of U.S. registry. 

The actions required by AD 2011–21– 

06, Amendment 39–16829 (76 FR 

64788, October 19, 2011), and retained 

in this proposed AD take about 1 workhour per product, at an average labor 

rate of $85 per work-hour. Based on 

these figures, the estimated cost of the 

actions that are required by AD 2011– 

21–06 is $85 per product. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $340, or $85 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2011–21–06, Amendment 39–16829 (76 

FR 64788, October 19, 2011), and 

adding the following new AD: 

BAE SYSTEMS (Operations) Limited: Docket 

No. FAA–2015–1279; Directorate 

Identifier 2014–NM–049–AD. 

(a) Comments Due Date 

We must receive comments by June 22, 

2015. 

(b) Affected ADs 

This AD replaces AD 2011–21–06, 

Amendment 39–16829 (76 FR 64788, October 

19, 2011). 

(c) Applicability 

This AD applies to all BAE SYSTEMS 

(Operations) Limited Model 4101 airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05. 

(e) Reason 

This AD was prompted by the need to 

reduce the life limit of certain main landing 

gear components, and to add certain postrepair inspections of critical structure to the 

maintenance/inspection program. We are 

issuing this AD to prevent failure of certain 

structurally significant items, including the 

main landing gear and nose landing gear, 

which could result in reduced structural 

integrity of the airplane; and to prevent fuel 

vapor ignition sources, which could result in 

a fuel tank explosion and consequent loss of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Maintenance Program Revision, 

With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–21–06, Amendment 

39–16829 (76 FR 64788, October 19, 2011), 

with no changes. Within 90 days after 

November 23, 2011 (the effective date of AD 

2011–21–06): Revise the maintenance 

program by incorporating Subjects 05–10–10, 

‘‘Airworthiness Limitations’’; 05–10–20, 

‘‘Certification Maintenance Requirements’’; 

and 05–10–30, ‘‘Critical Design Configuration 

Control Limitations (CDCCL)—Fuel System’’; 

of Chapter 05, ‘‘Airworthiness Limitations,’’ 

of the BAE Systems (Operations) Limited 

Jetstream Series 4100 Aircraft Maintenance 

Manual (AMM), Revision 35, dated February 

15, 2011. The initial compliance times for the 

tasks are at the applicable times specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 

Doing the actions required by paragraph (i) 

of this AD terminates the requirements of this 

paragraph. 

(1) For replacement tasks of life limited 

parts specified in Subject 05–10–10, 

‘‘Airworthiness Limitations,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited Jetstream 

Series 4100 AMM, Revision 35, dated 

February 15, 2011: Prior to the applicable 

flight cycles (landings) or flight hours (flying 

hours) on the part specified in the 

‘‘Mandatory Life Limits’’ column in Subject 

05–10–10, or within 90 days after November 

23, 2011 (the effective date of AD 2011–21– 

06, Amendment 39–16829 (76 FR 64788, 

October 19, 2011)), whichever occurs later. 

(2) For structurally significant item tasks 

specified in Subject 05–10–10, 

‘‘Airworthiness Limitations,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited Jetstream 

Series 4100 AMM, Revision 35, dated 

February 15, 2011: Prior to the accumulation 

of the applicable flight cycles specified in the 

‘‘Initial Inspection’’ column in Subject 05– 

10–10, or within 90 days after November 23, 

2011 (the effective date of AD 2011–21–06, 

Amendment 39–16829 (76 FR 64788, October 

19, 2011)), whichever occurs later. 

(3) For certification maintenance 

requirements tasks specified in Subject 05– 

10–20, ‘‘Certification Maintenance 

Requirements,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited Jetstream 

Series 4100 AMM, Revision 35, dated 

February 15, 2011: Prior to the accumulation 

of the applicable flight hours specified in the 

‘‘Time Between Checks’’ column in Subject 

05–10–20, or within 90 days after November 

23, 2011 (the effective date of AD 2011–21– 

06, Amendment 39–16829 (76 FR 64788, 

October 19, 2011), whichever occurs later; 

except for tasks that specify ‘‘first flight of the 

day’’ in the ‘‘Time Between Checks’’ column 

in Subject 05–10–20, the initial compliance 

time is the first flight of the next day after 

doing the revision required by paragraph (g) 

of this AD, or within 90 days after November 

23, 2011 (the effective date of AD 2011–21– 

06), whichever occurs later. 


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(h) Retained Restrictions on Alternative 

Actions, Intervals, and/or CDCCLs, With a 

New Exception 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–21–06, 

Amendment 39–16829 (76 FR 64788, October 

19, 2011), with a new exception. Except as 

required by paragraph (i) of this AD, after 

accomplishing the revision required by 

paragraph (g) of this AD, no alternative 

actions (e.g., inspections), intervals, and/or 

CDCCLs may be used unless the actions, 

intervals, and/or CDCCLs are approved as an 

alternative method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(i) New Maintenance or Inspection Program 

Revision 

Within 90 days after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable, by 

incorporating Subjects 05–10–10, 

‘‘Airworthiness Limitations’’; 05–10–20, 

‘‘Certification Maintenance Requirements’’; 

and 05–10–30, ‘‘Critical Design Configuration 

Control Limitations (CDCCL)—Fuel System’’; 

of Chapter 05, ‘‘Airworthiness Limitations,’’ 

of the BAE Systems (Operations) Limited J41 

AMM, Revision 38, dated September 15, 

2013. The initial compliance times for the 

tasks are at the applicable times specified in 

paragraphs (i)(1), (i)(2), and (i)(3) of this AD. 

Doing the actions required by this paragraph 

terminates the requirements of paragraph (g) 

of this AD. 

(1) For replacement tasks of life limited 

parts specified in Subject 05–10–10, 

‘‘Airworthiness Limitations,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited J41 AMM, 

Revision 38, dated September 15, 2013: Prior 

to the applicable flight cycles (landings) or 

flight hours (flying hours) on the part 

specified in the ‘‘Mandatory Life Limits’’ 

column in Subject 05–10–10, or within 90 

days after the effective date of this AD, 

whichever occurs later. 

(2) For structurally significant item tasks 

specified in Subject 05–10–10, 

‘‘Airworthiness Limitations,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited J41 AMM, 

Revision 38, dated September 15, 2013: Prior 

to the accumulation of the applicable flight 

cycles specified in the ‘‘Initial Inspection’’ 

column in Subject 05–10–10, or within 90 

days after the effective date of this AD, 

whichever occurs later. 

(3) For certification maintenance 

requirements tasks specified in Subject 05– 

10–20, ‘‘Certification Maintenance 

Requirements,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited J41 AMM, 

Revision 38, dated September 15, 2013: Prior 

to the accumulation of the applicable flight 

hours specified in the ‘‘Time Between 

Checks’’ column in Subject 05–10–20, or 

within 90 days after the effective date of this 

AD, whichever occurs later; except for tasks 

that specify ‘‘first flight of the day’’ in the 

‘‘Time Between Checks’’ column in Subject 

05–10–20, the initial compliance time is the 

first flight of the next day after doing the 

revision required by paragraph (j) of this AD, 

or within 90 days the effective date of this 

AD, whichever occurs later. 

(j) New Restrictions on Alternative Actions, 

Intervals, and/or (CDCCLs) 

After the maintenance or inspection 

program, as applicable, has been revised as 

required by paragraph (i) of this AD, no 

alternative actions (e.g., inspections), 

intervals, and/or CDCCLs may be used unless 

the actions, intervals, and/or CDCCLs are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (l) of 

this AD. 

(k) Credit for Previous Actions 

This paragraph restates the provisions of 

paragraph (j) of AD 2011–21–06, Amendment 

39–16829 (76 FR 64788, October 19, 2011). 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before November 23, 

2011 (the effective date of AD 2011–21–06), 

in accordance with Subjects 05–10–10, 

‘‘Airworthiness Limitations’’; 05–10–20, 

‘‘Certification Maintenance Requirements’’; 

and 05–10–30, ‘‘Critical Design Configuration 

Control Limitations (CDCCL)—Fuel System’’; 

of Chapter 05, ‘‘Airworthiness Limitations,’’ 

of the BAE Systems (Operations) Limited 

Jetstream Series 4100 AMM, Revision 33, 

dated February 15, 2010; which are not 

incorporated by reference in this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–1175; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 

(i) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(ii) AMOCs approved previously for AD 

2011–21–06, Amendment 39–16829 (76 FR 

64788, October 19, 2011), are not approved 

as AMOCs with this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or BAE Systems (Operations) 

Limited’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0043, dated 

February 21, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–1279. 

(2) For service information identified in 

this AD, contact BAE SYSTEMS (Operations) 

Limited, Customer Information Department, 

Prestwick International Airport, Ayrshire, 

KA9 2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 1292 

675704; email RApublications@

baesystems.com; Internet http://

www.baesystems.com/Businesses/

RegionalAircraft/index.htm. You may view 

this service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on April 29, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–11023 Filed 5–7–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1277; Directorate 

Identifier 2014–NM–155–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A319, A320, and A321 

series airplanes. This proposed AD was 

prompted by fatigue testing that 

determined fatigue damage could 

appear on clips, shear webs, and angles 

at certain rear fuselage sections and 

certain frames. This proposed AD is 

intended to complete certain mandated 

programs intended to support the 

airplane reaching its limit of validity 

(LOV) of the engineering data that 

support the established structural 

maintenance program. This proposed 

AD would require replacing the clips, 

the shear webs, and angles, including 

doing all applicable related investigative 


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